Results
94-07-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that requires modification of the cavity vent drain tube assembly at the center wing lower auxiliary fuel tank cavity. This amendment is prompted by a report that the cavity vent tube, if not properly grounded, could act as an electrical path in the event of a lightning strike. The actions specified by this AD are intended to prevent arcing in the tank cavity and possible resulting fire.
92-16-08: 92-16-08 BOEING: Amendment 39-8317. Docket No. 92-NM-08-AD. \n\n\tApplicability: Model 747 series airplanes; equipped with escape slides listed in Boeing Service Bulletin 747-25-2132, dated September 17, 1971; or equipped with escape systems installed in accordance with Supplemental Type Certificate SA574GL, SA575GL, SA744GL, SA745GL, or SA1215EA; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent jamming of an emergency exit door, accomplish the following: \n\n\t(a)\tFor airplanes equipped with escape slides listed in Boeing Service Bulletin 747-25-2132, dated September 17, 1971; and for airplanes equipped with escape systems installed in accordance with Supplemental Type Certificate (STC) SA574GL, SA575GL, SA744GL, or SA745GL: Within 20 months after the effective date of this AD, replace the plastic pulley guards on the emergency slide system packboard release mechanism, Boeing part number (P/N) 69B51507-1 and -2, with metal pulley guards, Boeing P/N 69B54562-1 and -2, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(b)\tFor airplanes equipped with escape systems installed in accordance with STC SA1215EA: Within 20 months after the effective date of this AD, replace the plastic pulley guards on the emergency slide system packboard release mechanism, Boeing part number (P/N) 69B51507-1 and -2, with metal pulley guards, Boeing P/N 69B54562-1 and -2, in accordance with Air Cruisers Service Bulletin 25-139, Revision 1, dated September 18, 1991; or in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(e)\tThis amendment becomes effective on September 16, 1992.
92-02-17: 92-02-17 BOEING: Amendment 39-8154. Docket No. 91-NM-145-AD. \n\n\tApplicability: Model 747 series airplanes, listed in Boeing Service Bulletin 747-25- 2754, dated March 30, 1989, certificated in any category. \n\n\tCompliance: Required within the next 24 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the girt bar end fittings from disengaging the girt bar floor brackets, accomplish the following: \n\n\t(a)\tReplace the girt bar floor brackets with modified brackets, in accordance with Boeing Service Bulletin 747-25-2754, dated March 30, 1989. \n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(d)\tThe replacement requirements of this AD shall be done in accordance with Boeing Service Bulletin 747-25-2754, dated March 30, 1989. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\t(e)\tThis amendment (39-8154, AD 92-02-17) becomes effective on March 2, 1992.
93-09-07: 93-09-07 PACIFIC SCIENTIFIC COMPANY, HTL/KIN-TECH DIVISION: Amendment 39-8573. Docket 93-NM-37-AD. This AD supersedes AD 93-08-06, Amendment 39-8553. \n\n\tApplicability: Fire extinguishers, as listed in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993; as installed on, but not limited to, Airbus Industrie Model A300, A310, and A320 series airplanes, Boeing Model 757-200 series airplanes equipped with Rolls Royce engines, and McDonnell Douglas Model DC-9-80 (MD-80) and MD-11 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent failure of a fire extinguisher to discharge extinguishant in the event of a fire, accomplish the following: \n\n\t(a)\tPrior to the accumulation of 500 hours time-in-service or within 60 days after the effective date of this AD, whichever occurs first, unless accomplished within the last 8 months prior to the effective date of this AD, perform a test ofthe low pressure indicating circuit to monitor actuation of the pressure switch on the fire extinguisher in accordance with the Accomplishment Instructions in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. \n\n\t\t(1)\tIf the switch passes the test, no further action is required by this AD. \n\n\t\t(2)\tIf the switch fails this test, prior to further flight, replace the fire extinguisher with a serviceable extinguisher. This replacement extinguisher must have been inspected previously in accordance with paragraph 3 of the Accomplishment Instructions in the service bulletin. \n\n\t(b)\tAs of the effective date of this AD, no person shall install, on any airplane, a Pacific Scientific fire extinguisher having a part number listed in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993, that has not been inspected previously in accordance with paragraph 3 of the Accomplishment Instructions in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. \n\n\t(c)\tFor switches that fail to pass the test required by paragraph (a) of this AD: Within 30 days after accomplishing the test, submit a report of the results of the test to the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425; or fax to (310) 988-5210. The report must include the following information: \n\n\t\t(1)\tWhen was the inspection performed? \n\n\t\t(2)\tWhat is the part number of the fire extinguisher? \n\n\t\t(3)\tWhat is the airplane model and series from which the extinguisher was removed? \n\n\t\t(4)\tWhere was the extinguisher installed (e.g., Position/Location: left engine, right engine, auxiliary power unit (APU) compartment, etc.)? \n\n\t\t(5)\tWhen was the last hydrostatic check performed on that extinguisher? \n\n\t\t(6)\tWho performed the last hydrostatic check on that extinguisher? \n\n\t\t(7)\tWhen was the last hex key check (low pressure indicating circuit test) performed onthat extinguisher? \n\n\t\t(8)\tWas the extinguisher guard tack welded, completely welded, or not welded to the switch housing? The information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. \n\n\t(d)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. \n\n\t(e)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(f)\tThe testing and replacement shall be done in accordance with Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. This incorporation by reference was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51, as of May 11, 1993 (58 FR 21912, April 26, 1993). Copies may be obtained from Pacific Scientific Company, HTL/Kin-Tech Division, Attention: Product Support Department, 1800 Highland Avenue, Duarte, California 91010. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425; or at the Office of the Federal Register, 800 North Capitol Street,NW., suite 700, Washington, DC. \n\n\tThis AD supersedes AD 93-08-06, Amendment 39-8553. \n\n\t(g)\tThis amendment is effective May 11, 1993.
91-08-03: 91-08-03 SIKORSKY AIRCRAFT: Amendment 39-6958. Docket No. 91-ASW-05. Applicability: All Sikorsky Aircraft Model S-76A helicopters, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent fatigue failure of the vertical pylon forward spar, which could result in loss of the helicopter, accomplish the following: (a) Within the next 25 hours time in service determine if forward spar cap angles, part numbers (P/N's) 76201-05001-103 and 76201-05001-104, are installed and if it is equipped with Sikorsky Modification Kit 76070-20086, then-- (1) If the affected helicopter has Sikorsky Modification Kit 76070-20086 installed, no further action is necessary; however (2) If the affected helicopter has the original unmodified forward spar cap angles with 1,395 or more hours time in service after the effective date of this AD, comply with paragraph (c), unless already accomplished, and thereafter at intervals notto exceed 1,420 hours time in service. NOTE: Information pertaining to Kit 76070-20086 is contained in Sikorsky Alert Service Bulletin No. 76-55-12. (b) For those helicopters with the original unmodified forward spar cap angles specified in paragraph (a)(2) with less than 1,395 hours time in service after the effective date of this AD, compliance with paragraph (c) is required prior to accumulation of 1,420 hours time in service, unless already accomplished, and thereafter at intervals not to exceed 1,420 hours time in service. (c) Remove and replace the forward spar cap angles with new parts of the same part numbers. (d) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance with the AD may be accomplished. (e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance or adjustment of the compliance times, which provides an equivalent level of safety, may be used if approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. This Amendment (39-6958, AD 91-08-03) becomes effective on May 3, 1991.
89-26-01: 89-26-01 BOEING: Amendment 39-6416. Docket No. 89-NM-139-AD. \n\n\tApplicability: Model 767 series airplanes listed in Boeing Service Bulletin 767-32-0081, dated April 27, 1989, certificated in any category. \n\n\tCompliance: Required within the next 750 landings after the effective date of this AD or prior to the accumulation of 15,000 landings, whichever occurs later, unless previously accomplished. \n\n\tTo prevent partial loss of braking and, potentially, the complete loss of braking, accomplish the following: \n\n\tA.\tReplace aluminum brake metering valve module shafts with steel shafts, in accordance with Boeing Service Bulletin 767-32-0081, dated April 27, 1989. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\tNOTE: The request should be forwarded through an FAA Principal MaintenanceInspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6416, AD 89-26-01) becomes effective on January 12, 1990.
77-23-05: 77-23-05 SCOTTISH AVIATION, LTD. (Formerly BEAGLE AVIATION, LTD.): Amendment 39-3076. Applies to Beagle Model B206 Series 1 and Series 2 airplanes, certificated in all categories. Compliance is required as indicated. To prevent possible fatigue failure of the outer wing, wing center section, and empennage assemblies, accomplish the following: (a) Prior to the accumulation of 11,000 hours total time in service on the outer wing, wing center section, or empennage assemblies, replace the affected assembly with an assembly of the same part number, or a part number approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, which has accumulated less than 11,000 hours total time in service. (b) Operators who have not kept records of hours of time in service on any assembly to which a provision of this AD applies shall substitute airplane hours time in service in lieu thereof. (Scottish Aviation, Limited, Mandatory Service Bulletin No. B206/54, dated October 21, 1975, covers the same subject.) This amendment becomes effective December 10, 1977.
75-19-03: 75-19-03 BOEING: Amendment 39-2366. Applies to all Boeing Model 747 series aircraft certificated in all categories. Compliance required as indicated unless already accomplished. \n\tTo prevent possible lavatory fire, accomplish the following: Within 300 hours time in service from the effective date of this AD, unless already accomplished, remove capacitor assembly from toilet flush motor and cap exposed wires in accordance with Boeing Service Bulletin 747-38-2021, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective September 19, 1975.
59-06-07: 59-06-07 VICKERS: Applies to All Viscount Model 745D Aircraft. Compliance required by April 1, 1960. In order to preclude the possibility of foreign object jamming primary flight controls in the cockpit floor, cover plates must be installed over all openings, in accordance with Vickers- Armstrongs Modification Bulletin NR.D.2146 Parts (B), (C), (D), (E), (F), and (P), or equivalent. Modifications D.1185 and D.2272 also cover sealing openings in the cockpit floor area.
54-19-02: 54-19-02 SIKORSKY: Applies to All Model S-55 Helicopters. Compliance required before October 1, 1954. To insure against the loosening of the servo pilot valve locknut and subsequent improper servo operation, safety clips, Sikorsky P/N S-14-40-5194, should be installed and safetied to P/N S14-40-3227-24 lockwasher. (Sikorsky Service Information Circular 1440-458 covers this same subject.)
69-05-02: 69-05-02 FAIRCHILD: Amendment 39-729 as amended by Amendment 39-1588 is further amended by Amendment 39-2641. Applies to FH-227 Type Airplanes Certificated in all categories. Compliance required as indicated. To detect the development of cracks in the wing area, accomplish the following: (a) Within 25 hours time in service after the accumulation of the specified hours in service, unless already accomplished, inspect or continue to inspect in accordance with Fairchild Service Bulletin 51-1, as amended by Revision 6, of December 12, 1975 or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region or with an approved equivalent inspection. (b) Where a visual inspection may be accomplished in lieu of x-ray, at least a 10-power glass must be used. (c) For those aircraft incorporating Fairchild Service Bulletin 51-1, Appendix No. 1, dated January 5, 1973, or an approved equivalent special structural inspection and alteration, the inspection interval for the outer wing panel without cracks remains at 1200 hours. If any cracks were discovered prior to the alteration the inspection interval will be that specified in paragraph 1.D(1) of the Appendix. (d) If new cracks are found or if repaired cracks are found to be propagating, replace the cracked part with a part of the same part number or with an approved equivalent part, or incorporate an approved repair before further flight. However, upon request, with descriptive information of the crack and proposed operating limitations submitted through an FAA maintenance inspector, the flight of the airplane in accordance with FAR 21.197 to a base where the repair can be made, may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Equivalent inspection, repairs or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (f) Upon request, with substantiating data submittedthrough an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Amendment 39-729 was effective March 12, 1969. Amendment 39-1588 was effective January 31, 1973. This amendment 39-2641 is effective June 18, 1976. NOTE: Amendment 39-2641 was distributed on June 7, 1976, as AD 76-12-04. The issuing office intended Amendment 39-2641 to be published as a revision to AD 69-5-2. Accordingly, the AD is being republished to reflect the correct AD number and AD 76-12-04 is cancelled.
68-05-02: 68-05-02 BRANTLY: Amdt. 39-572. Applies to Models B-2, B-2A and B-2B series helicopters with serial numbers 4 through 482 inclusive and Brantly Model 305 helicopters with serial numbers 1002 through 1045 inclusive. Compliance required as indicated. To prevent failure of the tail rotor drive shaft, accomplish the following: (a) Within 10 hours' time in service after receipt of this Airworthiness Directive, unless already accomplished, inspect the tail rotor drive shaft for corrosion using a borescope and treat it with a corrosion preventive compound in accordance with Brantly Service Bulletin, SB No. B2B-68-2, dated February 24, 1968, or FAA-approved equivalent. After treatment, and before the tail rotor drive shaft plug is installed, reinspect the tail rotor drift shaft, using a borescope, to assure that the entire internal surface of the shaft is completely covered with the corrosion preventive compound. (b) If corrosion is found as a result of the inspection required by paragraph (a) of this Airworthiness Directive which cannot be removed or leaves pits visible without magnification, disregard the treatment required by paragraph (a) of this Airworthiness Directive and prior to further flight replace the tail rotor drive shaft with a replacement part which complies with Brantly Service Bulletin, SB No. B2B-68-2, dated February 24, 1968, or FAA-approved equivalent. This amendment becomes effective March 30, 1968
57-03-03: 57-03-03 DOUGLAS AND LOCKHEED: Applies to Lockheed Constellation Series and Douglas DC-7 Series Airplanes. \n\n\tCompliance required by April 1, 1957, for Constellation aircraft and by May 1, 1957, for DC-7 aircraft. \n\n\tUnder certain cold weather operating conditions the perforated paper covering around the Purolator micronic filter elements are subject to accumulation of ice as a result of entrained water crystals in the fuel freezing on this covering. This interferes with proper fuel filtering by causing the fuel to pass through the bypass valve in the filter unit. To make the micronic filter less susceptible to clogging by ice, the perforated paper covering around the filter element is to be removed. Removal of the perforated cover does not affect the filtering characteristics of the filter element. Filter elements without the paper covering are identified as Purolator P/N 30868-3.
67-23-04: 67-23-04 FAIRCHILD-HILLER: Amdt. 39-458, Part 39, Federal Register August 5, 1967. Applies to Model F-27J Airplanes, Serial Numbers 111, and 113 through 121, inclusive and FH-227 Series Airplanes, Serial Numbers 501 through 520, inclusive. Incorporating Solar Auxiliary Power Unit, Model T62T25. Compliance required within the next 400 hours' time in service after the effective date of this AD, unless already accomplished. To prevent electrical damage to the A.C. engine-driven generator resulting from an unregulated and unloaded condition when the APU-driven generator (A.C.) is switched on the line, accomplish the following: (a) Rewire the engine-driven A.C. generator control sensing circuit in accordance with Fairchild-Hiller F-27 Service Bulletin 30-12, Revision No. 1, dated September 15, 1966, for F-27J aircraft and Fairchild-Hiller FH-227 Service Bulletin 30-1 dated August 23, 1966, for FH-227 aircraft, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or perform an equivalent rewiring modification, approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request, with substantiating data submitted through an FAA maintenance inspector, an increase in the compliance time may be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment effective August 31, 1967.
55-15-04: 55-15-04 DOUGLAS: Applies to all DC-6 Series Airplanes Below fuselage No. 487 Equipped With Hamilton Standard Propellers. \n\n\tCompliance required by first scheduled engine change after November 1, 1955, but not later than November 1, 1956. \n\n\tTo increase the integrity of the propeller feathering system in the event of a powerplant fire, all existing propeller feathering lines located forward of the firewall must be replaced with lines and flexible hose assemblies which will meet current fireproof and fire resistant requirements. \n\n\t(a)\tReplace the existing flexible hose portion of the feathering line between the union on the forward pipe assembly and the elbow on the inner ring with a new hose assembly Aeroquip P/N 304004-10-17 1/2. Douglas General Service Letter DC-6 No. 206 dated August 26, 1954, covers this subject. Resistoflex SSFR-3800-10 hose assembly and Aeroquip 309009-10S hose assembly are also considered acceptable for this application. \n\n\t(b)\tThe existing flexible hose assembly connecting to the governor is not affected by this directive. \n\n\t(c)\tRemove the existing short 304 sleeves or flexible metal sleeve from the feathering pump supply line, Aeroquip P/N 304002-16D-12 3/8, and install a fireproof cover, Douglas P/N 3500614-1. Douglas General Service Letter DC-6 No. 206 dated August 26, 1954, covers this subject. Aeroquip 601000 hose assembly equipped with Aeroquip 304 full length protective sleeve or Aeroquip 680-16S hose assembly equipped with Aeroquip 304 short sleeves covering the end fittings are also considered acceptable for this application.
55-23-03: 55-23-03 LOCKHEED: Applies to Models 49, 149, 649, 749 and 1049 Aircraft, Serial Numbers 1963 Through 1980, 2021 Through 2088, 2503 Through 2590, 2610, 2611, and 2614 Through 2677, 4001 Through 4024, 4163 Through 4166, 4501 Through 4581, 4583 Through 4594, 4602 Through 4604, and 4613 Through 4615. Compliance required as indicated. 1. As soon as possible, but not later than next 250 hours conduct magnetic particle or magnaglow inspections on main landing gear downlock spring cylinder assembly rod end P/N 295168 for cracks in the threaded portion. If cracks are found replace the part immediately. Repeat inspection, magnetic particle or 20-power magnifying glass at 300-hour intervals until replacement in accordance with paragraph 2 is accomplished. 2. Replace downlock spring cylinder assembly P/N 270104 with new assembly P/N 475211 as soon as practical but not later than the next progressive or base overhaul period approximately 2,500 hours. Concurrently with this replacement, line ream the lugs on the downlock strut assembly to (0.3770 inch-0.3780 inch) diameter and replace the spacer P/N 268225-2 with bushing P/N LS3859-4-1094 and replace bolt AN 23-21 with AN 23-22 attaching the lower end of the spring cylinder assembly to the downlock strut. (Lockheed Service Bulletins 49/860 and 1049/2709 also cover this subject.)
71-05-03: 71-05-03 BEECH: Amendment 39-1159 as amended by Amendment 39-1222 is further amended by Amendment 39-1244. Applies to Models A60 (Serial Numbers P123, P127 through P167), and all 99 series airplanes (Serial Numbers U-1 through U-136) approved for flight into known icing conditions. Compliance: Required as indicated, unless already accomplished. To prevent operation under unsafe environmental conditions, accomplish the following: A) Effective immediately, operation of the airplane in known icing conditions is prohibited. B) Prior to further flight, modify the existing operating limitations placard located on the righthand side wall adjacent to the copilot oxygen outlet on Beech Model A60 airplanes and located on the overhead panel on all Beech 99 series airplanes to read as follows: THIS AIRPLANE IS NOT APPROVED FOR FLIGHT IN KNOWN ICING CONDITIONS. C) On Beech Models A60 airplanes, install either transducer unit, P/N 3E1793, P/N 190-1, or P/N 190-2 in accordance with Beech Service Instruction 0430-355, Rev. 1, or by the accomplishment of any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. D) On all Beech 99 series airplanes, install transducer unit P/N 795-1 in accordance with Beechcraft Service Instructions No. 0378-355, or by the accomplishment of any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. E) Upon accomplishment of the modifications provided in Paragraphs C or D, compliance with the provisions of Paragraphs A and B is no longer required. NOTE: The Airplane Flight Manuals and Type Certificate Data Sheets for these model airplanes will be amended to reflect these changes. Amendment 39-1159 became effective March 2, 1971. Amendment 39-1222 became effective June 3, 1971. This Amendment 39-1244 becomes effective July 16, 1971.
93-16-13: 93-16-13 AEROSTAR INTERNATIONAL, INC.: Amendment 39-8697. Docket No. 93-CE-44-AD. Applicability: Models RX-6, RX-7, RX-8, RXS-8, S-40A, S-49A, S-50A, S-52A, S-55A, S-57A, S-57S, S-60S, S-60A, S-66A, S-71A, S-77A, 78C, 90C, QUBE-80, CTS, W100LB, 110P, and SPII balloons (all serial numbers), certificated in any category, that are equipped with hoses identified with one of the following: o AEROQUIP FC321-06 UL 5/16 LP-GAS HOSE 350 MAX. OPER. PSI 1Q92; o AEROQUIP FC321-06 UL 5/16 LP-GAS HOSE 350 MAX. OPER. PSI 2Q92; o AEROQUIP FC321-06 UL 5/16 LP-GAS HOSE 350 MAX. OPER. PSI 3Q92; o AEROQUIP FC321-06 UL 5/16 LP-GAS HOSE 350 MAX. OPER. PSI 4Q92; or o If hose identification is not legible. Compliance: Required as indicated after receipt of this AD, unless already accomplished. To prevent an uncontained fire in the balloon basket caused by a leaking fuel hose, accomplish the following: (a) Prior to further flight, remove each fuel hose fromthe leather sleeve, and, at system pressure, sniff test the entire length of the hose for signs of leakage. These signs could include frosting or chilling. (1) If any sign of fuel leakage is found, prior to further flight, replace the entire fuel hose/manifold assembly with an approved assembly that includes hoses with markings different than that specified in the Applicability section of this AD. (2) If no sign of fuel leakage is found, perform this fuel leakage test prior to each flight thereafter until the replacement required by paragraph (b) of this AD is accomplished. (b) Within the next 10 hours time-in-service after the effective date of this AD, unless already accomplished in accordance with paragraph (a)(1) of this AD, replace the entire fuel hose/manifold assembly with an approved assembly that includes hoses with markings different than that specified in the Applicability section of this AD. (c) Replacing the entire fuel hose/manifold assembly as required by either paragraph (a)(1) or (b) of this AD eliminates the repetitive test requirement of this AD. NOTE 1: Aerostar Service Bulletin No. 132, dated August 12, 1993, references the actions required by this AD. For the sake of inclusiveness, the procedures presented in this service bulletin have been incorporated into this AD. (d) The test and fuel hose/manifold assembly replacement required by this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by Federal Aviation Regulations (FAR) 43.7, and must be entered into the aircraft records showing compliance with this AD in accordance with FAR 43.11. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Room 232, Des Plaines, Illinois 60018. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may concur or comment and then send it to the Manager, Chicago Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Chicago Aircraft Certification Office. (f) Replacement fuel hose/manifold assemblies and copies of the service bulletin referenced in NOTE 1 of this AD may be obtained from Aerostar International, Inc., 1812 E. Avenue, P.O. Box 5057, Sioux Falls, South Dakota 57117-5057. The service information may also be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (g) This amendment becomes effective on October 15, 1993, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-16-13, issued August 18, 1993, which contained the requirements of this amendment.
95-10-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11, -2A12, -2B16, and -2B19 series airplanes, that requires an inspection to verify the proper operation of the uplock latch of the air driven generator (ADG), and replacement of the uplock latch with a serviceable part, if necessary. This amendment also requires replacing the uplock assembly with a modified uplock assembly, and performing a rigging inspection. This amendment is prompted by a report indicating that, upon operation of the manual release system, the ADG did not deploy due to failure of the shaft pin. The actions specified by this AD are intended to prevent failure of the shaft pin, which could lead to the inability of the pilot to manually deploy the ADG when necessary (i.e., when an airplane's primary electrical power sources are lost and the ADG fails to deploy automatically).
76-07-11: 76-07-11 ALEXANDER SCHLEICHER: Amendment 39-2572. Applies to Model ASW-17 gliders, Serial Numbers 17001 through 17043, certificated in all categories. Compliance is required as indicated. To prevent water ballast from leaking into the fuselage area which could result in a loss of elevator control, accomplish the following: (a) Before further flight, install a placard in the vicinity of the water ballast system control to read as follows: "USE OF WATER BALLAST SYSTEM PROHIBITED." (b) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, comply with the following: (1) Install a standard 25 mm (1 inch) diameter hose clamp on each of the two polyvinylchloride (PVC) hoses to secure the two PVC hoses to the brass tubes that feed the water ballast exhausts which are located at the bottom of the fuselage behind the landing gear. (2) Inspect for clamp security by exerting a 10 pound pull on each PVC hose after securing clamps. (3) Install new clamps in place of those clamps which come loose following the inspection required by paragraph (b)(2) of this AD and inspect the replacement clamps in accordance with paragraph (b)(2) of this AD. (c) Upon compliance with paragraph (b) of this AD, the placard required by paragraph (a) of this AD may be removed. This amendment becomes effective April 22, 1976.
90-24-08: 90-24-08 FOKKER: Amendment 39-6805. Docket No. 90-NM-140-AD. Applicability: Model F-28 series airplanes, Serial Numbers 11003 to 11241, inclusive, and 11991 and 11992, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. For airplanes Serial Numbers 11008 through 11241: Inspect the fuselage lap joint at stringer 73 between frames 5305 and 9305, in accordance with Part 1 of Fokker Service Bulletin F-28/53- A94, Revision 1, dated July 5, 1989, and with the following schedule: 1. For airplanes that accumulated 32,000 landings or more as of August 18, 1989 (the effective date of Amendment 39-6284, AD 89-17-02), inspect within 2 days after August 18, 1989. 2. For airplanes that have accumulated fewer than 32,000 landings as of August 18, 1989, inspect within 60 days after August 18, 1989, or prior to the accumulation of 20,000 landings, whichever occurs later. B. Repeat the inspections required by paragraph A. of this AD at intervals not to exceed 1,000 landings. C. If cracks are found, repair prior to further flight, in accordance with Part 2 of Fokker Service Bulletin F28/53-A94, Revision 1, dated July 5, 1989. After repair, continue to inspect in accordance with Part 1 of the service bulletin, at intervals not to exceed 1,000 landings. D. Replace the lap joint at stringer 73 between frames 4900 through 9805, in accordance with the accomplishment instructions in Fokker Service Bulletin F28/53-95, Revision 1, dated February 16, 1990, according to the schedule below. Accomplishment of this modification terminates the requirement for the repetitive inspections required by paragraphs B. and C. of this AD. 1. For airplanes, Serial Numbers 11008 through 11241, inclusive: prior to the accumulation of 30,000 landings, or within one year after the effective date of this AD, whichever occurslater. 2. For airplanes, Serial Numbers 11003, 11004, 11006, 11991, and 11992: prior to the accumulation of 50,000 landings, or within one year after the effective date of this AD, whichever occurs later. E. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM- 113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton Washington. Airworthiness Directive 90-24-08 supersedes AD 89-17-02 (Amendment 39-6284) which superseded AD 89-07-01 (Amendment 39-6157). This amendment (39-6805, AD 90-24-08) becomes effective on December 17, 1990.
94-21-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 airplanes. This action requires repetitive tightening of the screws and quick-release fasteners on the wing/body fairing panels. This amendment is prompted by reports of loosened wing/body fairing panels. The actions specified in this AD are intended to prevent structural damage to the horizontal or vertical stabilizer and potential injury to persons on the ground due to loosened wing/body fairing panels that may separate from the airplane.
92-07-12: 92-07-12 BOEING: Amendment 39-8208. Docket No. 91-NM-164-AD.\n\n\tApplicability: Model 767 series airplanes, as listed in Boeing Service Bulletin 767-25-0137, Revision 1, dated May 9, 1991, certificated in any category.\n\n\tCompliance: Required within the next 18 months after the effective date of this AD, unless accomplished previously.\n\n\tTo ensure proper deployment of the off-wing escape system, accomplish the following:\n\n\t(a) Modify the off-wing escape system in accordance with Boeing Service Bulletin 767-25-0137, Revision 1, dated May 9, 1991.\n\n\t(b) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(c) Special flight permits maybe issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.\n\n\t(d) The modification shall be done in accordance with Boeing Service Bulletin 767-25-0137, Revision 1, dated May 9, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(e) This amendment becomes effective on May 4, 1992.
94-08-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model ATP series airplanes, that requires modification of the wiring for the electric-powered disconnect unit for the elevator control system and a subsequent functional test of the elevator control system. This amendment is prompted by an in-service report of damaged wire insulation in the electrical power circuit for the elevator disconnect unit, which resulted in grounding of the circuit and consequent uncommanded operation of the disconnect unit. The actions specified by this AD are intended to prevent uncommanded operation of the elevator disconnect unit, which would result in single elevator operation and, consequently, reduced controllability of the airplane.
78-22-05: 78-22-05 BEECH: Amendment 39-3329. Applies to the following models and serial number airplanes, certificated in all categories: \n\n\nMODEL\nSERIAL NUMBERS\n50\nH-1 through H-11\nB50, C50\nCH-12 through CH-360\nD50, D50A, D50B, D50C and D50E\nDH-1 through DH-347 \nE50\nEH-1 through EH-70\nF50\nFH-71 through FH-93, FH-95, FH-96\nG50\nGH-94, GH-97 through GH-119\nH50\nHH-120 through HH-149\nJ50\nJH-150 through JH-176\n65, A65, A65-8200\nL-1, L-2, L-6, LF-7, LF-8, LC-1 through LC-335\n70\nLB-1 through LB-35\n65-80, 65-A80, 65-A80-8800, 65-B80\nLD-1 through LD-511 \n65-88\nLP-1 through LP-28, LP-30 through LP-47\n65-90, 65-A90, B90, C90\nLJ-1 through LJ-797 \nE90\nLW-1 through LW-297\n99, 99A, A99A, B99\nU-1 through U-164\n100, A100\nB-1 through B-247 \nB100\nBE-1 through BE-55\n\n\tCOMPLIANCE: Required as indicated unless already accomplished. \n\n\tTo prevent partial loss of elevator control due to possible failure of elevator control push rods, in accordance with instructions set forth herein and in Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions, accomplish the following: \n\n\tA)\tOn the following airplanes: \n\n\nMODEL\nSERIAL NUMBERS\n50\nH-1 through H-11\nB50, C50\nCH-12 through CH-360 \nD50, D50A, D50B, D50C and D50E\nDH-1 through DH-347 \nE50\nEH-1 through EH-70\nF50\nFH-71 through FH-93, FH-95, FH-96\nG50\nGH-94, GH-97 through GH-119\nH50\nHH-120 through HH-149\nJ50\nJH-150 through JH-176\n65, A65, A65-8200\nL-1, L-2, L-6, LF-7, LF-8, LC-1 through LC-335\n70\nLB-1 through LB-35\n65-80, 65-A80, 65-A80-8800 and 65-B80\nLD-1 through LD-511 \n65-88\nLP-1 through LP-28 and LP-30 through LP-47\n65-90, 65-A90, B90 and C90\nLJ-1 through LJ-716 \nE90\nLW-1 through LW-222\n99, 99A, A99A and B99\nU-1 through U-164\n100, A100\nB-1 through B-233\nB100\nBE-1 through BE-23\n\n\tUpon the accumulation of 1,050 hours total time-in-service for airplanes with less than 1,000 hours total time-in-service on the effective date of this AD,or \n\n\tWithin 50 hours time-in-service after the effective date of this AD, for airplanes with more than 1,000 hours total time-in-service on the effective date of this AD, that have not complied with AD 70-18-02, or \n\n\tWithin 500 hours time-in-service after the last inspection in accordance with AD 70-18- 02, for airplanes with more than 1,000 hours total time-in-service that have complied with AD 70-18-02: \n\n\t\t1.\tReview the airplane maintenance records for entries showing that Beechcraft Service Instructions No. 0334-152, Revision II, has been complied with. If Revision II of the Service Instructions has not been complied with, accomplish Paragraph A)2 of this AD. If Revision II of the Service Instructions has been complied with, accomplish Paragraph A)3 of this AD within an additional 100 hours time-in-service after this finding. \n\n\t\t2.\tGain access to the elevator control push rods (reference Figures I and II of this AD) and visually inspect for the words "CORROSION PROOFED"ink stamped near the center of the rods. If the words "CORROSION PROOFED" are ink stamped on a rod, no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on the rods, remove the elevator control push rods, clean, dye penetrant and visually inspect, check for bows, apply corrosion preventative treatment, identify and reinstall, all in accordance with Part I of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\t\t3.\tGain access to the elevator control push rods (reference Figures I and II of this AD) and visually inspect for the words "CORROSION PROOFED" ink stamped near the center of each rod. If the words "CORROSION PROOFED" are ink stamped on a rod, then no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on any rod and new rods were not installed during compliance with Revision II of the Service Instructions, paint a black stripe around the center of each rod in accordance with Part II of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. If any new rods were installed during compliance with Revision II of the Service Instructions and the new rods are not ink stamped "CORROSION PROOFED", on each new rod so installed, remove the elevator control push rod, disassemble, inspect for corrosion preventative treatment and alignment, and if not found accomplished, apply the corrosion preventative treatment, identify, reassemble and reinstall, all in accordance with Part III of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\tB)\tOn the following airplanes: \n\n\nMODEL\nSERIAL NUMBERS\nC90\nLJ-717 through LJ-797\nE90\nLW-223 through LW-297\nA100\nB-234 through B-247 \nB100\nBE-24 through BE-55\n\n\tWithin 100 hours time-in-service after the effective date of this AD: \n\n\t\t1.\tGain access to the elevator control push rods (reference Figures Iand II of this AD) and visually inspect for the words "CORROSION PROOFED" ink stamped near the center of the rods. If the words "CORROSION PROOFED" are ink stamped on a rod, no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on the rods, remove the elevator control push rod tubes, disassemble, inspect for corrosion preventative treatment and alignment, and if not found accomplished, apply the corrosion preventative treatment, identify, reassemble and reinstall, all in accordance with Part III of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\tC)\tOn all airplanes affected by this AD, replace any elevator control push rods found cracked or otherwise unserviceable during any inspection required by this AD with serviceable rods that comply with the requirements of this AD prior to returning the airplane to service. \n\n\tD)\tAny equivalent means of compliance with this AD must be approvedby the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tThis AD supersedes AD 70-18-02, Amendment 39-907 (35 FR 305) as amended by Amendments 39-1074 (35 FR 13722 and 13723) and 39-1879 (39 FR 21120). \n\n\tThis amendment becomes effective November 6, 1978.